Convertible turbine-engine.



E. F. ABERNETHY.

CONVERTIBLE TURBINE ENGINE.

APPLICATION FILED MAY 15. I903. RENEWED on. 21. 1914. 1 1%8 813.

INVENTOR 2 SHEETS-SHEET I.

WITNESSES:

E. F. ABERNETHY. CONVERTIBLE TURBINE ENGINE.- APPLICATION mEn my 15. 1903. RENEWED OCT. 21. 1914.

1,148,813. v Patented Aug. 3, 1915.

2 SHEETS-SHEET 2.

- WITNESSES: INVENTOR W r zdu xnfifienzefy Y E w BY A rronms rs.

UNITED STATES PATENT OFFICE.

EDWIN F. ABERNETHY, OF NEW YORK, N. Y., ASSIGNOR OF ONE-HALF TO GEORGE H. ABERNETHY, OF BROOKLYN, NEW YORK.

CONVERTIBLE TURBINE-ENGINE.

Specification of Letters Patent.

Patented Aug. 3, 1915.

Application filed May 15, 1903, Serial No. 157,242. Renewed October 21, 1914. Serial No. 867,901.

To all whom it may concern:

Be it known that 1, Enwm F. ABERNETHY, a citizen of the United States, and a resident of the city of New York, borough of Brooklyn, 1n the county of Kings and State of New York, have invented a new and Improved Convertible Turbine- Engine, of which the following is a full, clear, and exact description.

My invention relates to improvements in turbine engines, and the chief object that I have in view is the provision of an improved construction adapted to be operated ciliciently by the admission of a motive fluid of any kind, such as steam, an explosive gaseous fluid, or compressed air, no modification being required in the structure of the engine when the character ,of the motive fluid is changed. Y

A further object that I have in view is the provision of special means forming an integral and indivisible part of the engine for producing, from an explosive gaseous mixture, a charge possessing the energy requisite for propulsion of the engine, thus embodying in one and the same apparatus means for translating the latent energy of fuel into rotary power. 1

A further object of the invention is the provision of a simple form of rotary valve mechanism by which the admission of an explosive fuel mixture to a firing chamber, and the passage of the resultant gases, following the explosion of the charge, to the rotary member of the turbine, is controlled by one and the same valve mechanism, thus insuring the operation of the parts in due order and materiallv simplifying the apparatus.

A further object, is to make the engine reversible atwill, so'that it will run either in a forward or a backward direction with equal facility and develop the same energy when rotating in either direction, the conditions attending the supply of motive fluid being uniform without regard to the direction in which the engine is running.

Further objects and advantages of the invention will appear in the course of the subjoined description, and the novelty will be defined by the annexed claims.

Reference is to be had to the accompanying drawings forming a part of this specification,'in which similar characters of reference indicate corresponding parts in all the figures.

Figure 1 is a longitudinal sectional elevatlon through a convertible turbine engine constructed in accordance with my invent1o n; Fig. 2 is an end elevation thereof; Fig. 3 1s a vertical cross section taken in the plane of the dotted line 33 of Fig. 1; Fig. 4 is a diagrammatic view illustrating the arrangement of the stationary groups of vanes and the revoluble propeller vanes; and Fig. 5 is a detail sectional elevation on an enlarged scale, through a type of clutch adapted to transmit the motion from the engine shaft to the shaft of a rotary valve mechamsm.

In carrying my invention into practice, I employ an elongated cylindrical shell or casing 5, adapted to be secured firmly in place by means of feet 6, and provided at its ends with heads 7, said heads being each made of a single casting, or the head may be cast in sections, as desired. The heads are provided with stuifing boxes 8 of any suitable pattern, and they are shown by Fig. 1 as having laterally-extending brackets 9 which support or carry the alined shaft bearings 10, the latter being of any suitable type, such for ixample as the roller bearings illustrated by l1 designates an engine shaft extending longitudinally and centrally through the shell 5, the stufling boxes 8, and the shaft bearings 10. This shaft is equipped with a drum or carrier 12, the latter being-made fast with said shaft and disposed longitudinally and centrally within the casing 5. This drum or carrier is equipped with a plurality of groups of propelling blades 13, 14, 15 and 16, although the number of groups may be varied by increasing or decreasing them according to the capacity of the engine. The groups of blades are spaced at suitable intervals one from the other, each group having its blades disposed in an annular row around the periphery of the drum or carrier so that annular spaces will be left between the approximate ends of the blades in adjacent groups, as clearly shown by Figs. 1 and 4. Each blade in each of the groups is of double reversed curvature; that is to say, one-half of the blade is curved in one direction to present an impact or working face 17, and the remaining half of the blade is curved in a reversed direction to present an opposite impact or working face 18; Each blade of all the groups of propelling blades is fastened securely in any approved way to the periphery of the drum or carrier 12, to occupy a diagonal pos1t1on thereon, and the blades of each group are disposed in parallel relation to form the tion to the groups of rotary propelling blades 13, 14, 15, 16. .The stationary vanes are secured in any suitable way to the easing 5, so as to occupy fixed positions therein, and thus the engine is equipped with alternating sets of curved propelling blades and stationary vanes, substantially as shown by Figs. 1 and'4. Each vane of the groups 20, 21, 22, consists of a flat straight plate secured in an inclined position to the inner surface of the casing 5, and occupying a di agonal relation to the longitudinal axis of the engine. The vanes of each statlonary group are disposed in parallel relation one to the other to produce a series of diagonal straight passages 23 for the free flow of the motive fluid, and these vanes andtheir complemental passages are inclined in an opposite direction to the propelllng blades and their passages 19. The number of groups or sets of stationary vanes is not material, but in the exemplification shown by Figs. 1 and 4, there are only three sets of vanes.

It is to be understood, however, that the number of sets of vanes will vary according to the number of groups of propelling blades employed in the-engine, although I may use additional sets of stationary vanes beyond the end groups of propelling blades 13, 16. The number of stationary blades in. each group varies with respect to the number of propelling blades in adjacent groups, and in the diagrammatic view of Fig. 4, the-diagonal vanes of each grouplargely exceed the number of double curved blades in adjoining groups, thus providing for the division of the motive fluid into currents adapted to strike diflerent portions of the propelling blades. 1

' The cylindrical casing 5 exceeds in length the drum 12 and the blades thereon, and this drum is disposed within the casing so as to leave passages or spaces 24, 25 for the admission and exhaust of the motive fluid.

' The engine casing 5 is provided on one side with a longitudinal exhaust chest 26,

which is provided with an exhaust chamber,

'27 and with fluid passages 28,29. Reversing valves 30, 31 are seated in the passages -28, 29 of the exhaust chest, for the purpose of controlling the flow of the motive fluid through the passage 28 to the engine supply passage 24, and the outflow of the exhausted motive fluid from the passage 25 to the assa e 29, and thenceto theexhaust chamer 2 from which the exhausted motive fluid may be conducted by a pipe or any other suitable means. The valves 30, 31, however, are adapted to be shifted by an means familiar to those skilled in the art, when it is. desired to reverse the direction of rotation of the turbine, and thus the mo tive fluid is adapted to be supplied bythe passages 29, 25, and to'be exhausted from the passages 24, 28, into the chamber 27.

32 designates a valve chest which is attached solidly to the exhaust chest 26 and is adapted to form an integraland indivisible part of the engine structure. This valve chest is equipped with means for the reception of a combustible mixture adapted to be exploded in order to form a gaseous charge which is admitted to and exhausted from the engine in a way to utilize the energy of said charge in the propulsion of the engine; and said valve chest is also equipped with means for controlling the inlet of the combustible vaporand' the outlet of the gases following the explosion of said vapor. The chest 32 is provided with a firing chamber 33, which extends longitudinally .of'the engine, and the end portions of this chamber are reduced in diameter to form the valve seats 34. The reduced ends of the valve chest are providedwith two inlet ports 35', 36, and with. the passages 37, 38, the latter having direct communication with the passages 28; 29 of the exhaust chest. The passages 37, 38 of the valve chest are/out of alinement vertically with the inletpassages 35, 36, and these four passages are controlled by the operation of valves 39, 40, the latter being of the rotary type and fitted to the seats 34 in the end portions of the valve chest.

The two valves 39, 40 are attached firmly to a horizontal valve shaft 41, which runs lengthwise through the valve chest and is supported in suitable bearings afl'orded by brackets 42, the latter being shown as-attached to the end portions of said chest. The

valves are tubularor hollow, each being closed at one end by a suitable head, Whilethe other end is open for communication with the firingchamber 33. Said valves 39, 40 are provided with ports 43, 44, said ports of one valve being disposed on one side while the ports of the other valve are disposed on the opposite side thereof, as shown by Fig. .1. The port43of each valve is adapted to have communication with one of the inlet ports 35 or 36, while the other port 44 of each valve is disposed alongside of the port 43 to lie'in a difl'erent vertical plane, and to adapt it' to have communication with one of the passages 37 or 38. The exhaust port 44 in each valve is somewhat longer than the inlet port 43 in the valve, so as to give the deslred clearance by making provision for the escape of the exploded charge just before the admission of a fresh charge into the firing chamber. The reversed arrange ment of the ports in' the two valves 39, 40, enables one valveas for example the valve 40to admit a combustible vapor into one end of the firing chamber 33, at the same time that the other valveas for example the valve 39-is adjusted for the escape of an exploded charge from said firing chamber 33, through the passages 37 28 into the engine by the passage 24. When the valves are turned a quarter turn from the position shown in Fig. 1, all the ports are out 01f, but the next quarter turn brings the inlet port of the valve 39 into registration with the port 35, and the outlet port 44 of the valve 40 into registration with the passage 38; but as the valve 31. remains in the closed position, the fluid cannot escape, and the valves continue to turn until the port 43 of the valve 40 registers with the port 36, so as to increase the supply of the combustible vapor in the firing chamber 33, thus admitting the combustible vapor through the valves successively and at bothends of the firing chamber 33. The charge is now exploded by a suitable igniter, the positionof which is indicated at 45, and the gases resulting from the explosion pass through the valve 39, the passages 37 28, and the passage 24, into the righthand end of the cylinder. The impact of the motive fluid against the first set of propelling blades 13 turns the blades and the drum 12. The gases escape from the passages of the blades 13 to the vanes 20, by which they are directed against the blades 14, and from thence the gases pass successively through the alternating stationary vanes and sets of propeller blades so as to drive the carrier or drum 12 and thus rotate the shaft 11. If it is desired to reverse the direction of rotation of the shaft, it is only necessary to shift the valves 30, 31, thus closing the passages 28,- 37 and opening the passages 38, 29, whereupon the m0- tive fluid produced by the explosion of the combustible vapor supplied to the firing chamber 33 will be admitted at proper intervals into the passage 25 at the left-hand end of the engine so as to operate against the set of blades 16, and thence successively pass through the alternating vanes and the blades from left to right of the engine, thereby driving the latter in a reverse direction.

The combustible vapor is adapted to be supplied to the firing chamber 33 on the alternate opening of the valves 39, 40, by

means of a feed pipe 46, the end portions of which are adapted for communication with the ports 35, 36, said feed pipe having check valves 47, 48 adapted to prevent the back pressure of gases resulting from the explosion in the chamber 33. In Figs. 1 and 1 her is at therein, and these pumps have their iston rods 49 operated by cams or eccentrlcs 50 on the engine shaft 11. The pumps 49, 50

have connection with a suitable source of gas or vapor supply (not shown), and on the up-stroke of the pump pistons the gas or vapor is drawn into the pumps to be expelled therefrom on the next downstroke of the pistons, whereby the pipes 51, 52 carry the gas or vapor in a compressed condition into the pipe 46, by which the vapor is supplied to the firing chamber on the alternate opening of the valves.

The igniter 45 may be of any suitable construction known to those sln'lled in the art. Provision is made for the injection of Water sprays into the firing chamber 33, for the purpose of extinguishing any sparks which may remain therein following the explosion of the combustible vapor; and to this end I provide a small water pipe 53, having nozzles or roses 54, disposed in the firing chamber. The water is adapted to be conveyed to the pipe 53 by means of a pipe 55, which leads to a Water pump 56 adapted to be operated by a cam or eccentric 57 on the engine shaft. Water sprayed into the firing chamonce vaporized by the heat of the chamber, but this water has a tendency to prevent undue heating of the parts. It is evident that the valve shell and the firing chamber may be enveloped by a water jacket, but for simplicity and lightness of construction I prefer to omit this jacket.

Engines of small capacity may be started by hand, as is ordinarily practised, but for engines of large size I find itdesirable to provide means for supplying. a compressed fluid to the engine before the vapor-exploding mechanism is brought into service. To

this end I have provided the apparatus with an air pump 58, adapted to be operated by a cam or eccentric 59 on the engine shaft. This air pump is connected by a pipe 60 with an air tank, and from the pump cylinder extends a pipe 61 which supplies air under pressure to a distributing pipe 62, the latter having outlets 63 in-the passages 37, 38 of the valve chest. It is evident that compressed air may be supplied by this pipe 62 to the passages 37 or 38, for the purpose of starting the engine and rotating the shaft 11, so as to bring the pumps and the other parts of the apparatus into service.

The rotary valves 39, 40 are adapted to be driven at the required speed by a transmitting mechanism operated from the engine shaft. The valve shaft 41 is provided on one end with a loose sprocket gear 64,

which is engaged by a sprocket chain 65 sprocket gear 64 by a spring 70, which is seated against the abutment 71, and one side of the slidable clutch 67, thus forcing the pin 68 into the socket 69 and making the gear 64 fast with the valve shaft 41 through the medium of the clutch 67 which is splined to said valve shaft. It is evident that the clutch 67 may be withdrawn by hand in order to free the stud 68 from the sprocket gear 64, and the valves will thus cease rotating because the sprocket gear 64 will run idly on the valve shaft 41. v

The pipes51, 52, 55 and 61 should be provided with valves or stop-cocks to control the passage 'of vapor, water'and air tothe several parts of the engine. By closing these valves the supply of vapor maybe cut off, and steam may be admitted to thechamber 33 by the pipe 46 or its equivalent. The steam is intended to be supplied to the engine under boiler pressure, and the admission of the steam to the chamber 33, and from'this chamberrinto theturbine engine, is controlled by the operation of the valves 39, 40, while the proper manipulation of the valves 30, 31, will change the direction of rotation of the shaft. It is not necessary.

in my convertible engine to alter or modify the structure of. the several parts in order to adapt it to be, driven by steam or compressed air, or the gases resulting from the explosion of a combustible vapor, and this convertible feature of the engine is of great importance because the apparatus may be driven by any available source of fluid supply.

In the operation of-my engine, the motive fluid whether steam, air or the gases resulting from the ignition of an explosive charge, are supplied at full pressure from chamber 33 to the turbine cylinder by the operation of the rotary valve mechanism, whereby efficiency is attained and economy of the motive fluid is secured. In the ordinary Corliss engine, the steam is admitted at full boiler pressure to the cylinders for effecting economy, whereas in the slide valve engine the steam is supplied to the cylinders under pressure considerably below the steam in the valve chest. My rotary valve mechanism operates to admit the motive fluid under full pressure to the turbine cylinder, 21. e. the motive fluid flowing into the turbine cylinder is practically at the'same pressure as the motive fluid in chamber 33, so that in case steam is supplied at full boiler pressure to chamber 33 as heretofore stated, then the steam will flow by the operation of the rotary valves at practically full boiler pressure into the turbine cylinder.

The speed of rotation of the turbine rotor is controlled by the speed of the rotary valve. As shown in Fig. 1, the rotary valve is driven by gearing from the engine shaft so asto rotate said valves at a slower speed than the speed of rotation of the engine rotor. Now as the motive fluid is admitted by the valves at the fullpressure to the turbine rotor, and as the valves rotate at a slower speed relatively to the speed of the turbine rotor, it follows that the desired economy of the motive fluid is attained and, further, that the speed of rotation of the turbine rotor is dependent upon and controlled at least in a measure by the valve mechanism, as a result of which the valve mechanism is adapted to be regulated as to speed in a manner to control the speed of rotation of the turbine rotor. I

It is to be understood that in driving the engine by steam, the set of pumps is thrown out of use and thus remains idle. The engine may be built to use steam as the motive fluid, in which case the pumps and other parts are omitted; but to drive the engine by a combustible gas, the pumps and accessories mustbe installed.

.My improved engine'may be employed with any kind ofexplosive fuel, either in gaseous or liquid form. It is self-starting, reversible, and equally effective in running either forward or backward. It is well adapted for use as a high-speed engine, although it can be operated at any desired speed by the employmentof means for controlling the supply of combustible vapor, or any other suitable governor, and therefore it is always under perfect control. The engine is smooth-running because I do not employ reciprocating parts which have a tendency to cause vibration, and furthermore the engine is noiseless, as there is no noise due to the exhaust of the motive fluid. The engine is thoroughly efficient and re liable, while economical in the consumption of fuel, and is of comparatively light weight, the latter being a very desirable feature, es: pecially when used as a marine engine. When steam is supplied to the turbine en.- gine it should be equipped with a suitable governor, which will make the engine run at uniform speed under any and all loads. The load may vary to any degree, but this.- will not affect the speed, because the governor operates tocontrol that feature. The" I way to utilize the inflowing charge in the firing chamber for the expulsion of the smoke and gases resulting from the explosion of the previous charge. Itwill be seen that with the valves in the positions shown by Fig. 1, the port 44 of the valve 39 registers with the passage 37, while the valve 40 is in a position where its port 43 registers with the inlet passage 36. Before'the parts take these positions, the charge in the chamber is exploded, and the combustible mixture admitted by the valve 43 expels the smoke and .gases resulting from this explosion, through the valve 39, and the passages 37, 28 and 24, into the right-hand end of the cylinder.

The pumps 49, 50 may be used to supply a combustible vapor and air respectively to the firing chamber, but the air pump 50 should be so timed that a charge of scavenging air will be admitted to the firing chamber immediately following the explosion of a charge of combustible vapor therein. This scavenging air expels the smoke and gases resulting from the explosion, and the air is mixed or combined with the next charge of the combustible vapor so as to secure an aerated mixture or vapor suitable for producing the explosion by the igniter on the next cycle of operations of the engine.

Having thus described my invention, I claim as new and desire to secure by Letters Patent: v

1. An explosive turbine engine provided with a cylinder, a rotary turbine member therein carrying groups of vanes, each vane being curved or inclined in reverse directions at the respective ends, other groups of stationary vanes within said cylinder, a firing chamber adapted to communicate with the chamber of said cylinder, means for compressing a combustible vapor and for supplying the same under pressure to said firing chamber, means for exploding the combustible vapor, valve mechanism separate from the aforesaid vapor compressing mechanism and adapted to control the flow of vapor into one end or the other of the cylinder, and another valve mechanism operating to admit exploded charges of vapor at intervals and under high pressure to the groups of vanes in the chamber of said cylinder.

2. An explosive turbine engine provided with a cylinder, a rotary turbine member therein carrying groups of vanes, said vanes having reversely curved surfaces, other groups of stationary vanes within said cylinder, a firing chamber adapted to communicate with the chamber of said cylinder, means for compressing a combustible vapor and for supplying the same under pressure to said firing chamber, means for exploding the combustible vapor, rotary valve mechanism intermediate the firing chamber and the cyl- .inder chamber, said valve mechanism being independent of the aforesaid vapor compressing and supplying mechanism, said valve mechanism operating to control the inflow of exploded gaseous charges at regular intervals into the cylinder chamber, whereby the rotary member is driven by successive impulses of highly compressed vapor, and another valve mechanism for admitting the vapor into one end or the other of said cylinder.

3. An explosive turbine engine provided with a cylinder, a rotary turbine member therein carrying groups of vanes, said vanes having reversely curved surfaces, other groups of stationar vanes within said cylinder, a firing cham er adapted to communicate with the chamber of said cylinder, means for compressing a combustible vapor and for supplying the same under pressure to said firing chamber, means for exploding I the combustible vapor, means for supplying an extinguishing medium to said firing chamber, whereby preignition of the vapor charges is precluded, means for controlling the flow-of exploded gases from the firing chamber to the turbine in the cylinder chamber, and separate valves for controlling the admission of the exploded gases into one end or the other of said cylinder.

4. A reversible turbine engine provided with a cylinder, a rotary turbine member therein carrying groups of double reversed blades, a pressure chamber adapted to communicate with the cylinder chamber, means for supplying motive fluid to said chamber, independent ports between the pressure chamber and the cylinder chamber at the respective'ends thereof, duplex valve mechanism controlling said ports and regulating the flow of motive fluid through either of them, and duplex reversing valve mechanism adapted to direct the flow of motive fluid through one portor the other whereby the turbine may be driven in one direction or the other. i I

5. In an explosive turbine, a cylinder, a revoluble turbine member, a group of blades carried by said turbine member, said blades having reversely curved or inclined working surfaces, means for compressing a gaseous charge, means for exploding said charge, means for admitting the gases resulting from the explosion of said charge to the cylinder, and separate means for controlling the direction of How of said gases whereby the gases may be admitted to the cylinder at one end or the other for driving the turbine member in one direction or the other.

6. In an explosive turbine, a cylinder, a revoluble turbine member, a group of blades surfaces, means for compressing a gaseous charge, means for explodlng said charge,

rotary valve mechanism for admitting at interva s to the cylinder the gases resulting from the explosion of successive charges, and separate valve mechanism controllable at will and adapted to control the direction of flow of the gases, whereby the turbine member maybe driven in one direction or the other. a

7. A turbine engine having a working chamber, a piston therein, a firing chamber having a plurality of inlet ports, passages connecting the, two chambers, and a plurality of chambered revoluble valves seated in the firing chamber and cooperating individually with said inlet ports, said valves being provided with ports adapted to register alternately with the inlet ports and the passages, one valve operating alternately with respect to the other valve in admitting a combustible charge to said firing chamber.

8. A turbine engine having a working chamber, a piston therein, a firing chamber having a plurality of inlet ports, passages between the two chambers, a valve shaft, a plurality of valves revoluble with-the shaft, each valve having ports which communicate alternately with one of said inlet,ports, and gearing for rotating the valve shaft.

9. In an engine of the class described, a turbine cylinder and a rotary piston positioned therein, a valve chamber separate from the piston cylinder and adapted to communicate therewith, valve mechanism positioned in said valve chamberfor controlling the communication between said chamber'and the piston cylinder, means for supplying a combustible fuel to said chamwalls of .the chambelgthe extinguishing liqher, means for exploding the combustible fuel within said chamber, and means for supplying an extinguishing liquid to said valve chamber for the purpose of extinguishing sparks therein and for cooling the uid being vaporized within said chamber and retained momentarily therein so as to become commingled with the succeeding charge to be produced in the chamber by the I explosion of combustible fuel in the latter.

10. A reversibleturbine engine having a piston cylinder, means for controlling. the

admission of a motive -fluid to'either end of said cylinder, a piston revoluble in said cylinder, and groups of propelling blades and of stationary vanes secured to said piston and the piston-cylinder, respectively, each propelling' blade having active surfaces at its respective ends, which surfaces are reversed to each other and are adapted to be exposed to the pressure ofthe motive fluid which is admitted to one end or the other of said cylinder.

.11. A' turbine engine having a worln'ng chamber, a piston revoluble therein, spaced groups of peripheral blades ranging in a general direction lengthwise of the piston and disposed in a diagonal position thereon,

and groups of vanes stationar in the chamblades, the number of vanes in each grou exceeding the number of blades in an a joining group.

12. A turbine enginehavingaworking chamber, a revoluble piston, propelling blades each havin a working surface at the respective ends 516113013, said surfaces of each blade being reversed to each other, and stationary vanes in coperative relation to said blades.

her and alternating with t e groups of 13. A turbine engine having a working the respective ends thereof, and groups of a stationary vanes alternating with said blades.

15. A reversible turbine engine having a working chamber, a revoluble piston, groups of peripheral propelling blades ranging lengthwise of said piston, each blade having rcversely deflected endportions and the blades of each group being disposed in sub- .stantially parallel relation one to the other,

and groups of stationary vanes alternating with said groups of blades; the vanes of each group being disposed obliquely to the blades of an adjacent group. 7

16. A reversible turbine engine comprising a piston chamber, means for admitting a motive fluid toeither end of said cylinder, a piston revoluble in the cylinder, groups of blades ranging lengthwise of said piston and each having reversed working faces at the respective ends thereof, vanes alternating with said" blades, a valve chamber, valves for intermittently controlling the supply of a combustible charge to said valve chamber and the passage of an exploded gaseous motive fluid to the piston cylinder, means for exploding a combustible charge in said 1 chamber, and a reversing valve mechanism for controlling at will the admission of an exploded charge of motive fluid to either end of the piston cylinder.

17. A reversible turbine engine comprising a piston cylinder, a piston provided with a plurality of groups of reversed double blades, groups of vanes within. said cylinder and in alternate order to said groups of piston blades, a firing chamber independent of the piston chamber, means for compressing a combustible vapor and supplying the same to said firing chamber, means for exploding a combustible charge in the firing chamber, and reversing means for controlling the pas- "sage of an exploded charge to either end of the piston cylinder whereby the turbine motor may be driven in one direction or the other.

18. A reversible explosive engine comprising a firing chamber, a piston chamber, a piston in the piston chamber, means for compressing and supplying charges of combustible vapor to said firing chamber, means for exploding said charges of vapor in said chamber, and means for controlling the admission of exploded vapor charges to either end of said piston chamber. 1

19. A reversible explosive turbine engine comprising a piston chamber, a revoluble piston provided with double reversed blades, vanes alternating with said double piston blades, a firing chamber, means for compressing and supplying a combustible vapor at intervals to said chamber, means for exploding the successive charges of vapor in said chamber, and means for admitting such exploded charges of vapor to one end or the other of the piston chamber, whereby the piston may be driven in one direction or the other by the impact or blast of the successive exploded charges of highpressure vapor admitted to one end or the other of the piston chamber.

20. A reversible explosive turbine engine comprising a piston-chamber, a revoluble piston ranging lengthwise of said chamber, said piston having groups, of doublereversed blades ranging lengthwise thereof, vanes alternating with said groups of reversed blades, a firing chamber independent of the piston chamber, means for compressing and supplying a combustible vapor to said firing chamber, means for exploding in the firing chamber said charges of combustible vapor, and means for controlling the admission of v the exploded high-pressure charges of vapor to either end of the piston cylinder, whereby the vapor is caused to act in one direction or the other against the reversed blades of said turbine piston.

21. In an engine of the class described, a turbine cylinder and a rotary piston positioned therein, a valve chamber separate from the piston cylinder and adapted to communicate therewith, rotary valve mechanism positioned within said valve chamber for controlling the communication between said chamber and the piston cylinder, means for supplying successive charges of liquid fuel and air to said chamber, means for igniting each charge within the chamber at a period when said valve mechanism operates to cut off communication between said valve cham ber and the piston cylinder, and means for charges in said chamber, a valve mechanism for controlling the outflow of the resultant gases from the explosive chamber to the piston chamber, and means for supplying compressed air as a motive fluid initially to the piston chamber and independently of the valve mechanism, for starting the operation of the piston.

23. In an engine of the class described, a turbine cylinder and a rotary piston positioned therein, a valve chamber separate from the piston cylinder and adapted to communicate therewith, pumps for supplying to said chamber air and combustible fuel in definite quantities so as to constitute a combustible charge, means for igniting the combustible charges supplied successively to said chamber, means for supplying to the valve chamber after each explosion therein a liquid for extinguishing any residual products of combustion and for cooling the walls of said chamber, and a rotary valve for automatically controlling the outflow of the vapor under pressure from said chamber and into the piston cylinder.

24. In an engine of the class described, a turbine engine embodying a cylinder and a rotary piston therein, a chamber separate from said cylinder and adapted to communicate therewith, pumps for successively supplying to the chamber air and combustible fuel in definite quantities so as to constitute combustible charges, means for igniting each combustible charge within the chamber, valve mechanism operating to control the inflow of the combustible charges to the chamber, said valve mechanism operating to also control the outflow from said chamber and into the engine cylinder of the vapor resulting from the ignition of the combustible charges within the chamber, and a separate pump for supplying scavenging air to said chamber at a period subsequent to ignition of the combustible charges and during the time when the valve mechanism operates to establish communication between the chamber and the piston cylinder. 7

25. In a turbine engine, a reversible piston having blades ranging lengthwise thereof, each blade having active surfaces at its respective ends, said surfaces being curved reversely to each other.

26. In a turbine engine, a reversible piston having blades, each blade having a-plurality of active surfaces which are reversely curved to one another.

27. In a turbine engine, a reversible piston having blades, the respective ends of which are curved in opposite directions and produce reversely-facing working surfaces.

28. In a turbine engine, a reversible piston having groups of blades, each of which is provided with a plurality of active surperipheral blades, each blade ranging di- 20' agonally withlrespect to the periphery of the piston, each blade having a plurality of active surfaces which are curved reversely, combined with a group of vanes in cooperative relation to the reversed surfaces of the respective groups of blades, said vanes being inclined oppositely to the blades.

31. In a turbine engine, a reversible piston provided with a plurality of groups of peripheral blades, each blade ranging diagonally with respect to the periphery of the piston, each blade having its end portions curved oppositely toproduce reversed active surfaces, combined with groups of vanes in cooperative relation to said reversed active surfaces of the respective groups of blades, said groups of vanes alternating with and inclinedoppositely to the groups of blades. I p

32. A turbine engine comprising a piston chamber, a shaft extending therethrough, a piston on said shaft and provided with peripheral blades, a motive fluid chamber, a valve-shaft extending through the motive fluid chamber, means for supplying motive to said chamber, a plurality of valves carried by the shaft and each having two sets of ports for alternately admitting motive fluid to the chamber and the. outflow of an exploded gaseous charge to the piston chamber, the ports of one valve being reversely arranged to the ports of the other valve, and means for rotating the valve shaft from the piston shaft.

33. A turbine engine comprising a piston chamber, a shaft extending therethrough, a piston on said shaft and provided with peripheral blades, a motive fluid chamber, a valve-shaft extending through the motive fluid chamber, means for supplyingmotive fluid to said chamber, a plurality of valves seated in said motive fluid chamber and revoluble with said valve shaft, said valves being arranged to admit motive fluid at intervals to. said chamber and to regulate the interval of its outflow from the chamber to the piston chamber, gearing for rotating the valve shaft from the iston shaft, and means controllable at will or throwing the valve shaft into and out of gear with the piston shaft. or I r 34. A reversible turbine engine comprismg a cylinder chamber, a rotary turbine member provided with double reversed blades, stationary vanes in cooperative re lation to said blades, a pressure chamber adapted to be supplied with motive fluid, and reversing valve mechanism operating to admitsaid motive fluid into either .end of the turbine situated within said cylinder ehamber, whereby the turbine may bedriven in one direction or the other. r

a firing chamber independent of said motor, means for compresslng an explosive vapor v and supplying the same to said firing chamber, means for exploding said vapor in said chamber, means for supplying an .extin operable to feed definite quantities of'air.

. 35. The combination of a turbine motor,-

mechanism positioned to control the passages between said cylinder and the .combustion chamber, said valve mechanism operating to shut oif'the passages when the air and gas pumps are efiective in .supplying the mixture to the combustion chamber, means for igniting the gaseous mixture contained within the combustion chamber, and means for operating said valve mechanism substantially at the period of ignition of the gaseous mixture whereby the resulting vapor under high pressure is free to flow into the cylinder and propel the turbine piston therein.

37. In an engine, the combination of .a

cylinder, a reversible turbine piston operable therein, a-combustion chamber separate from the cylinder and connected with the respective ends thereof, means for generating within the combustion chamber a vapor under high pressure adapted to be utilized in imparting rotary motion to'said turbine piston, and valve mechanism for controlling the flow of said vapor into one end of the-cylinder for driving-the turbine piston in one direction andin'to the other end of said cylinder for reversing the direction of rotation of the turbine piston.

38. In an explosive turbine, the combination with a turbine cylinder and a rotor cooperating therewith, of a combustion chamber separate from the turbine cylinder and connected therewith, a pump connected with said combustion chamber for feeding thereto a combustible ,vapor in definite quantities and at stated intervals, an air comp'essor connected to said combustion chamr for supplying air at stated intervals thereto, and means for igniting the combustible charges produced by the air and combustible vapor supplied by the compressor and the pump respectively.

39. In an explosive turbine, the combination with a turbine cylinder and a rotor cooperating therewith, of acombustion chamber separate from said turbine cylinder and connected therewith for feeding charges of exploded vapor to the same, a gas pump connected with said combustion chamber for feeding thereto a combustible gas at stated intervals and in definite quantities, an air compressor connected to the combustion chamber for supplying air thereto at predetermined intervals, means. for igniting the combustible charges produced by the air and gas supplied by the compressor and pump respectively, and means for controlling the communication between the combustion chamber and the turbine cylinder, said controlling means closing the communication between said chamber and the cylinder at {)he time of feeding air and gas to the cham- 40. In an explosive turbine, the combination with a turbine cylinder and a rotor cooperating therewith, of a combustion chamber separate from the cylinder and connected therewith, means for feeding a combustible vapor to said chamber, means for feeding air to said chamber, an igniter for exploding the charges produced by feeding the combustible vapor and air to said chamber, controlling means between the chamber and said cylinder, and means for feeding to the combustion chamber an extinguishing medium adapted to eliminate sparks of residual combustible matter produced by the explosion of the combustible charges within said chamber.

.41. An explosive turbine en e embodying a cylinder provided with an inlet port and an exhaust port, a rotor positioned within the cylinder, said rotor being provided with peripheral blades, stationary blades positioned within the cylinder and alternating with said blades of the rotor, a combustion chamber connected through the inlet port with said cylinder, an air compressor connected with said combustion chamber, a gas compressor also connected with said combustion chamber, said air compressor and gas compressor operating to supply definite charges of air and gas to the chamber for producing therein a gaseous charge, means for igniting said gaseous charge within the combustion chamber to produce therein a motive fluid under high pressure, and means for controlling the'flow of the resulting motive fluid to the cylinder for exertingpressure upon the blades so as to impart motion to the rotor.

42. In an engine of the class described, the combination of a turbine rotor and a cylinder in which said rotor is operable, a pressure chamber separate from said cylinder and in which chamber is adapted to be contained a motive fluid under a predeter mined pressure, rotary mechanism cooperating with the turbine cylinder and the pressure chamber for periodically admitting to the turbine cylinder the motive fluid at approximately the pressure prevailing in said pressure chamber, and means for imparting to the valve mechanism a speed of rotation relatively slower than the speed of rotation of the turbine rotor.

In testimony whereof I-have signed my name to this specification in the presence of two subscribing witnesses.

EDWIN F. ABERNETHY.

Witnesses: p

G. H. ABERNETHY, H. T. BERNHARDL 

